Mars Global Surveyor: Aerobraking Mission Overview

Lyons, Daniel T.; Beerer, Joseph G.; Esposito, Pasquale; Johnston, Mark; Willcockson, William H.

doi:10.2514/2.3472

Cited by 68 publications

(27 citation statements)

References 6 publications

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“…Such off-design panel deployment occurred during the aerobraking of the MGS, 23 which led to a complete reworking of its aerobraking strategy. For the configuration presented in this paper, the effect of differential panel deployment on the trajectory was studied.…”

Section: Sensitivity To Panel Deploymentmentioning

confidence: 99%

Trajectory and Attitude Simulation for Aerocapture and Aerobraking

Kumar

Tewari

2005

Journal of Spacecraft and Rockets

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A combined strategy of aerocapture and aerobraking is presented to achieve a near-circular orbit, starting from a hyperbolic trajectory, without requiring an orbital insertion burn. Aerothermodynamic force, moment, and heat flux calculations employ a Maxwellian free-molecular flow model, with Knudsen-number-based interpolations for the transition regime. The six-degree-of-freedom motion model, including quaternion-based attitude dynamics, allows stability and sensitivity analyses for the atmospheric passes. A spacecraft model with two large panels suitable for Earth aerocapture is considered. Minor orbit-correction burns at the apoapsis are provided after each pass for manipulating the periapsis for the next pass to meet the desired aerobraking corridor. It is observed that an initial orbit of eccentricity 1.6 and relative entry velocity of 12 km/s at 300-km altitude can be reduced to an orbit with an eccentricity of 0.02, using a total of six atmospheric passes, without exceeding the peak convective heat flux constraint for the spacecraft or requiring an orbit insertion burn. This result has considerable importance for low-Earth-orbit space-tug captures and Mars missions, wherein the strategy proposed will lead to significant savings in spacecraft propellant mass during the orbit insertion and, subsequently, orbit circularization. Nomenclature= orbital eccentricity F = external force vector, ∈ 3 × 1 J = inertia tensor of the spacecraft, ∈ 3 × 3 J 11 , J 22 , J 33 = principal moments of inertia of the spacecraft K n = Knudsen number M = external moment vector, ∈ 3 × 1 m = mass of the spacecraft n i = unit normal vector of the ith surface panel p, q, r = angular velocity components about the X , Y , and Z body axes Q = convective heat load on the spacecrafṫ Q = convective heat fluẋ Q max = maximum convective heat flux q 0 , q 1 , q 2 , q 3 = quaternion components used to describe body orientation R = distance of spacecraft center of mass from the planet's center r i = position vector of the ith panel centroid relative to the center of mass of the spacecraft, r i ∈ 3 × 1 S(ω) = skew-symmetric matrix, ∈ 3 × 3 s = molecular speed ratio T W /T ∞ = ratio of wall temperature to freestream temperature V = spacecraft velocity measured in the planet fixed coordinate system X fo , Y fo , Z fo = forces along the wind axes α = angle of attack

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Section: Sensitivity To Panel Deploymentmentioning

confidence: 99%

Trajectory and Attitude Simulation for Aerocapture and Aerobraking

Kumar

Tewari

2005

Journal of Spacecraft and Rockets

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“…3 During the real aerobraking, the periapsis altitude will wave due to the large uncertainties in the local atmospheric density (see Fig. 4) [12] . In order to produce enough drag to accomplish aerobraking, the periapsis altitude will be maintained within a specified corridor with acceptable limits for the spacecraft heating and dynamic pressure.…”

Section: Resultsmentioning

confidence: 99%

“…In order to produce enough drag to accomplish aerobraking, the periapsis altitude will be maintained within a specified corridor with acceptable limits for the spacecraft heating and dynamic pressure. For example, at the main phase of the MGS [12] aerobraking, the upper limit of the spacecraft dynamic pressure corridor is 0.68 N/m 2 . In terms of the above calculation results in Fig.…”

Section: Resultsmentioning

confidence: 99%

Spacecraft aerodynamics and trajectory simulation during aerobraking

Zhang

Han

Zhang

2010

Appl. Math. Mech.-Engl. Ed.

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This paper uses a direct simulation Monte Carlo (DSMC) approach to simulate rarefied aerodynamic characteristics during the aerobraking process of the NASA Mars Global Surveyor (MGS) spacecraft. The research focuses on the flowfield and aerodynamic characteristics distribution under various free stream densities. The variation regularity of aerodynamic coefficients is analyzed. The paper also develops an aerodynamics-aeroheating-trajectory integrative simulation model to preliminarily calculate the aerobraking orbit transfer by combining the DSMC technique and the classical kinematics theory. The results show that the effect of the planetary atmospheric density, the spacecraft yaw, and the pitch attitudes on the spacecraft aerodynamics is significant. The numerical results are in good agreement with the existing results reported in the literature. The aerodynamics-aeroheating-trajectory integrative simulation model can simulate the orbit transfer in the complete aerobraking mission. The current results of the spacecraft trajectory show that the aerobraking maneuvers have good performance of attitude control.

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“…[5]), problems concerning the aerobraking (e.g. [6]) and linked to the release of landers and rovers (e.g. [7]).…”

Section: Introductionmentioning

confidence: 99%

Long dwell time orbits for lander-based Mars missions

Ortore

Circi

2015

Aerospace Science and Technology

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Please cite this article in press as: E. Ortore et al., Long dwell time orbits for lander-based Mars missions, Aerosp. Sci. Technol. (2015), http://dx.doi.org/10. 1016/j.ast.2015.06.026 This is a PDF file of an unedited manuscript that has been accepted for publication. As a service to our customers we are providing this early version of the manuscript. The manuscript will undergo copyediting, typesetting, and review of the resulting proof before it is published in its final form. Please note that during the production process errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain. 1 Long dwell time orbits for lander-based Mars missionsEmiliano Ortore*, Christian Circi*, Gian Luigi Somma** AbstractThis paper deals with the possibility of retrieving orbits around Mars able to provide long dwell times over a given area of the planet, without needing expensive orbital corrective manoeuvres. After a general description of the fundamental principles associated with the obtainment of the repeating ground track orbits which satisfy the aforesaid requirement, the concepts have been applied to Mars to gain trajectories which make it possible to maximize the daily contact time between a probe orbiting around the planet and a lander on the surface. The lander has been considered as equipped with an antenna of 0.5 m of diameter, working in the bands C, X, Ku, and the cases of both fixed and mobile antenna have been taken into account.

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Mars Global Surveyor: Aerobraking Mission Overview

Cited by 68 publications

References 6 publications

Trajectory and Attitude Simulation for Aerocapture and Aerobraking

Trajectory and Attitude Simulation for Aerocapture and Aerobraking

Spacecraft aerodynamics and trajectory simulation during aerobraking

Long dwell time orbits for lander-based Mars missions

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